Deployment and actuation mechanisms
A mechanism for rotating a missile control surface 6 about an axis 26 from
the illustrated stowed position within the missile to a deployed position
in which it extends radially from the missile axis M--M and for then
turning the surface about radial axis 13 so as to steer the missile. A
single drive motor 22 is coupled by worm 20 to a bevel gear 18 mounted in
a bracket 12, the bracket being turnable about axis 13 with respect to a
fixed support 10. The control surface 6 is fixed via arm 23 to a bevel
gear 24, which gear is mounted to the bracket 12 for rotation about axis
26 and is engaged with gear 18. While the surface 6 is stowed, a sprung
locking pin 14 carried by the bracket 12 is held in engagement with
support 10 by gear 18 so that rotation of the motor 22 rotates gear 18
with respect to bracket 12 and hence rotates gear 24 along with arm 23 and
control surface 6 about axis 26. When the surface so comes to its deployed
position, a hole 25 in gear 18 becomes aligned with pin 14 and the pin
moves into the hole so fixing gear 18 with respect to the bracket.
Rotation of the shaft of motor 22 then produces rotation of bracket 12,
gear 18 and surface 6 about axis 13.
The mechanism can be used in other situations where it is required to erect
a member from a stowed position to one of a range of operative positions
and to then move the member within that range.
Goulding; Kenneth (Stevenage, GB2) |
British Aerospace PLC
April 9, 1986|